A supercharger turbine rotating shaft

Abstract

The utility model discloses a kind of supercharger turbine rotating shaft, applied in turbine performance test, including turbine, rotor shaft and shaft end locking nut;Rotor shaft is connected with rotor shaft by shaft end locking nut;Turbine includes turbine hub;Turbine hub has central through hole in central position;Multiple turbine blades are distributed on the front side surface of turbine hub;The front section and middle section of rotor shaft have rotor shaft main body;The front end of rotor shaft main body has outer thread section and mounting shaft section;Mounting shaft section is located in the rear side of outer thread section;Mounting shaft section is through the central through hole of turbine;Outer thread section cooperates with shaft end locking nut and locks turbine;The middle part of rotor shaft main body has positioning step for positioning and supporting turbine;The utility model is applied in turbine performance test, by the design of the utility model, it is favorable to quickly and reliably obtain turbine blade performance data, and then quickly verify whether turbine blade performance reaches pre-required design index, improve turbine design development timeliness.

Description

Technical Field

[0001] This utility model relates to the field of turbocharger technology, and in particular to a turbocharger turbine shaft, specifically a turbocharger turbine shaft used for performance testing. Background Technology

[0002] Traditional engines generate power by burning fuel in the cylinder. Since the amount of fuel input is limited by the amount of air drawn into the cylinder, the power output of the engine is also limited. If you want to increase the output power, you can only increase the amount of fuel by compressing more air into the cylinder, thereby improving the combustion efficiency.

[0003] A turbocharger is a mechanical device that increases engine power output without changing engine efficiency, while simultaneously reducing fuel consumption. In recent years, engine turbocharging technology has developed rapidly, playing a vital role in reducing emissions, increasing power, and improving high-altitude performance.

[0004] For turbochargers, the turbine impeller is the core component. The turbine uses the energy of engine exhaust gas to drive the turbine shaft to rotate. The turbine shaft is a complex part that is made of cast high-temperature alloy turbine and rotor shaft welded together by electron beam. The high-temperature alloy turbine is the key to the aerodynamic performance. Different turbine blade structures will produce different turbine flow performance.

[0005] Currently, the traditional method for obtaining turbine performance data is through experimentation. This requires manufacturing a turbine shaft containing turbine blades and then conducting physical experiments under the conditions of the entire turbocharger unit. These experiments typically use engine exhaust temperature conditions, with the test gas temperature selected at 600–650°C. For details on obtaining experimental data, please refer to [link to relevant documentation]. Figure 7 As shown, the main workflow includes: First, the design and fabrication of turbine casting molds; Second, the design of the turbine structure based on turbine blade design data; Third, the design and manufacture of turbine precision casting molds; Fourth, the precision casting production of turbine castings; Fifth, the welding and machining of turbine shafts; Sixth, the machining of turbine shafts; Seventh, the overall assembly and testing of turbine shafts; Eighth, the acquisition of turbine performance data.

[0006] As can be seen from the above steps, obtaining turbine blade performance data requires a huge investment of time and incurred high manufacturing costs. If the turbine blade performance fails to meet design specifications, another round of manufacturing experiments will be conducted, multiplying the costs.

[0007] Therefore, there is an urgent need to develop a technology that can solve the above-mentioned technical problems. Utility Model Content

[0008] The purpose of this invention is to address the technical deficiencies of existing technologies by providing a turbocharger turbine shaft.

[0009] Therefore, this utility model provides a turbocharger turbine shaft, which is used in turbine performance testing, and includes a turbine, a rotor shaft and a shaft end locking nut;

[0010] The rotor shaft is detachably and fixedly connected to the rotor shaft by a locking nut at the shaft end;

[0011] The turbine includes the turbine hub;

[0012] The turbine hub has a longitudinally distributed central through hole at its center;

[0013] Multiple turbine blades are distributed around the front surface of the turbine hub;

[0014] Multiple turbine blades are evenly distributed around the vertical central axis of the turbine hub, along the circumference of the turbine hub.

[0015] The rotor shaft has a stepped shaft structure.

[0016] The front and middle sections of the rotor shaft have the rotor shaft body;

[0017] The front end of the rotor shaft body has an external thread section and a mounting shaft section;

[0018] The mounting shaft section is located behind the external thread section;

[0019] The mounting shaft section extends longitudinally through the center bore of the turbine.

[0020] The external thread section is used to lock the turbine together with the shaft end lock nut;

[0021] The rotor shaft body has a positioning step in the middle;

[0022] The positioning step is used to position and support the turbine;

[0023] Multiple turbine blades are identical in shape and size;

[0024] For turbines, each turbine blade has an air intake side on the side away from the turbine hub;

[0025] The rear end of the blade intake edge is fixedly connected to the front surface of the turbine hub;

[0026] Each turbine blade has an exhaust edge on one side near the front end face of the turbine hub;

[0027] The inner end of the blade's outlet edge is fixedly connected to the front surface of the turbine hub.

[0028] As can be seen from the technical solution provided by this utility model above, compared with the prior art, this utility model provides a turbocharger turbine shaft with a scientific design. This utility model is applied to turbine performance testing. Through the design of this utility model, it is beneficial to quickly and reliably obtain turbine blade performance data, and then quickly verify whether the turbine blade performance data meets the pre-required design indicators, significantly saving design and development time costs, improving the efficiency of turbine design and development, and having significant practical significance.

[0029] Furthermore, this invention provides a low-cost and rapid technical solution for obtaining turbine blade performance test results. It allows the use of a low-cost aluminum alloy turbine instead of a traditional cast turbine to manufacture the turbine shaft, thereby enabling rapid acquisition of turbine blade performance through testing. Attached Figure Description

[0030] Figure 1 A three-dimensional structural diagram of a turbocharger turbine shaft provided for this utility model;

[0031] Figure 2 A partial cross-sectional structural diagram of a turbocharger turbine shaft provided for this utility model;

[0032] Figure 3 A three-dimensional structural diagram of the turbine used in a turbocharger turbine shaft provided by this utility model;

[0033] Figure 4a A three-dimensional structural diagram of the shaft end locking nut used in a turbocharger turbine shaft provided by this utility model;

[0034] Figure 4b A schematic diagram of the front side structure of the shaft end locking nut used in the turbocharger turbine shaft provided by this utility model;

[0035] Figure 4c A cross-sectional view of the shaft end locking nut used in a turbocharger turbine shaft provided by this utility model;

[0036] Figure 5 A side view of the rotor shaft used in a turbocharger turbine shaft provided by this utility model;

[0037] Figure 6 A flowchart illustrating the testing method for a turbocharger turbine shaft provided by this utility model;

[0038] Figure 7 A flowchart of a traditional design, production, and verification method for turbine shafts;

[0039] In the diagram, 1 is the turbine, 2 is the rotor shaft, and 3 is the shaft end lock nut.

[0040] 11. Turbine hub; 12. Central through hole; 13. Turbine blade; 14. Vertical central axis; 15. Hub planar structure.

[0041] 131. Inlet edge of the blade; 132. Outlet edge of the blade;

[0042] 20. Rotor shaft body; 21. External thread section; 22. Positioning step; 23. Mounting shaft section;

[0043] 31. End face planar structure; 32. Internal thread structure. Detailed Implementation

[0044] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0045] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0046] In the description of this patent, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection or setting, a detachable connection or setting, or an integral connection or setting. Those skilled in the art can understand the specific meaning of the above terms in this patent according to the specific circumstances.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0048] See Figures 1 to 3 , Figures 4a to 4c , Figures 5 to 6 This utility model provides a turbocharger turbine shaft for use in turbine performance testing, which includes a turbine 1, a rotor shaft 2 and a shaft end locking nut 3;

[0049] The rotor shaft 2 is detachably fixed to the rotor shaft 2 by means of the shaft end locking nut 3;

[0050] Among them, turbine 1 includes turbine hub 11;

[0051] The turbine hub 11 has a longitudinally distributed central through hole 12 at its center;

[0052] Multiple turbine blades 13 are distributed around the front surface of the turbine hub 11;

[0053] Multiple turbine blades 13 are evenly distributed around the vertical central axis 14 of the turbine hub 11 in the circumference of the turbine hub 11.

[0054] Among them, rotor shaft 2 is a stepped shaft structure;

[0055] The front and middle sections of the rotor shaft 2 have a rotor shaft body 20;

[0056] The front end of the rotor shaft body 20 has an external thread section 21 and a mounting shaft section 23;

[0057] Mounting shaft section 23 is located behind external thread section 21;

[0058] The mounting shaft section 23 extends longitudinally through the center through hole 12 of the turbine 1;

[0059] The external thread section 21 is used to lock the turbine 1 together with the shaft end lock nut 3;

[0060] The rotor shaft body 20 has a positioning step 22 in the middle;

[0061] The positioning step 22 is used to position and support the turbine 1.

[0062] In this invention, specifically, the multiple turbine blades 13 are all identical in shape and size;

[0063] In this utility model, specifically, for the turbine 1, each turbine blade 13 is provided with a blade inlet side 131 on the side away from the turbine hub 11;

[0064] The rear end of the blade intake edge 131 is fixedly connected to the front surface of the turbine hub 11;

[0065] Each turbine blade 13 has a blade outlet edge 132 on one side near the front end face of the turbine hub 11;

[0066] The inner end of the blade outlet edge 132 (i.e. the side facing the turbine hub 11) is fixedly connected to the front surface of the turbine hub 11.

[0067] It should be noted that, for this utility model, the turbine blade 13 is a three-dimensional blade with spatial twist, and each turbine blade 13 has a blade inlet edge 131 and a blade outlet edge 132.

[0068] In a specific implementation, one embodiment can be: the blade inlet edge 131 serves as the turbine inlet leading edge, and its shape and structure are parallel to the vertical central axis (i.e., the rotation center line) 14 of the turbine hub 11.

[0069] In a specific implementation, another embodiment can be: the blade inlet edge 131 serves as the turbine inlet leading edge, and its shape and structure are inclined structures that are not parallel to the vertical central axis 14 (i.e., the rotation center line) of the turbine hub 11.

[0070] Furthermore, the angle between the blade intake edge 131 and the vertical central axis 14 (i.e., the rotation center line) of the turbine hub 11 is 0 to 40 degrees.

[0071] It should be noted that, for this utility model, the blade inlet edge 131 serves as the turbine inlet leading edge, and its shape has a structure that is parallel or inclined along the vertical central axis (i.e., the rotation center line) 14, thereby obtaining different inlet airflow angle conditions.

[0072] In specific implementation, turbine 1 is preferably an aluminum alloy turbine; the material of turbine 1 is aluminum alloy, and the processing method is five-axis machine tool milling. The specific material of turbine 1 can be high-strength aluminum alloys such as 2618 (2618A) or 2A70.

[0073] In specific implementation, the front end face of the hub 11 is the hub planar structure 15;

[0074] The hub planar structure 15 is used to contact the end face planar structure 31 on the rear side of the shaft end locking nut 3 and the two are connected by a fixed torque.

[0075] In this utility model, specifically, for the rotor shaft 2, the external thread section 21 is used to lock the turbine 1 together with the shaft end locking nut 3. The specific structural design is as follows:

[0076] The external thread of the external thread section 21 is threadedly fixedly connected to the internal thread structure 32 (i.e., internal thread) of the shaft end locking nut 3;

[0077] In practice, the diameter of the positioning step 22 is larger than the diameter of the central through hole 12 of the turbine 1;

[0078] The front surface of the positioning step 22 is a plane.

[0079] In practice, the mounting shaft section 23 is installed in conjunction with the center through hole 12 of the turbine 1;

[0080] The mounting shaft section 23 and the center through hole 12 of the turbine 1 are transition fit.

[0081] It should be noted that the dimensions of the mounting shaft section 23 and the dimensions of the center through hole 12 of the turbine 1 are in a transition fit tolerance relationship.

[0082] In practice, the rotor shaft 2 is made of alloy steel, specifically 40Cr or 42CrMo alloy steel. Its end has a threaded structure (i.e., external thread section 21), and it also has an installation shaft section 23 that mates with the turbine center through hole and a positioning step 22 for installing the turbine.

[0083] In this utility model, specifically, the shaft end locking nut 3 includes a rear end face planar structure 31 and an internal thread structure 32 located at the center position.

[0084] The internal thread structure 32 is an internal thread hole that passes vertically through the shaft end locking nut 3.

[0085] It should be noted that the internal thread structure 32 of the shaft end locking nut 3 can be locked and connected with the thread structure (i.e., the external thread section 21) on the rotor shaft 2, thereby fixing the turbine 1 that passes through the rotor shaft 2.

[0086] In practice, the material of the shaft end locking nut 3 is alloy steel, specifically 40Cr or 42CrMo alloy steel. It has an end face plane structure 31, which can achieve an effective fixed position connection between the turbine and the rotor shaft by applying axial rotation torque, thus meeting the requirement that the turbine and rotor shaft have no relative displacement when the turbine shaft rotates at high speed.

[0087] It should be noted that the shaft end locking nut 3 is locked to the rotor shaft 2 by the thread (specifically the external thread section 21), which can fix the turbine 1 through the center through hole of the rotor shaft, so that the turbine shaft of the overall turbocharger can meet the requirements of high-speed rotation.

[0088] In this invention, specifically, a turbocharger turbine shaft is provided for use in low-temperature performance testing, where the required test temperature range is 50–200°C.

[0089] See Figure 6 As shown, in order to verify the performance of the turbocharger turbine shaft provided by this utility model, this utility model also provides a test method for the turbocharger turbine shaft. This method is a design, production, and verification workflow for the turbine shaft, which includes the following steps:

[0090] The first step is to construct the airfoil of turbine blade 13 of turbine 1; that is, to design the airfoil of turbine impeller blade.

[0091] The second step is to obtain a three-dimensional model of the aluminum alloy turbine 1 based on the blade profile of the turbine blade 13 constructed in the first step; that is, to carry out the aluminum turbine structure design based on the turbine blade design data.

[0092] It should be noted that in the first and second steps, the blade profile (i.e., 3D model) of the turbine blade 13 of turbine 1 can be designed using a computer in a traditional manner, and a 3D model of turbine 1 can be obtained. For example, the conventional design method for a turbine impeller can be as follows: First, based on the aerodynamic performance requirements, the control curves of the turbine shroud and hub are designed, and the hub and shroud surfaces are formed by rotation to meet the turbine strength requirements. Then, based on the turbine aerodynamic performance, the corresponding turbine blades are designed. The turbine blades are connected to the turbine hub surface, and the blade root and hub surface are transitioned by an arc, ultimately forming the overall turbine structure. Of course, other existing conventional design methods can also be used, which will not be elaborated here.

[0093] The third step involves obtaining the turbine 1 made of aluminum alloy by milling based on the three-dimensional model of turbine 1 obtained in the second step, as well as obtaining the rotor shaft 2 and the shaft end locking nut 3 by milling.

[0094] It should be noted that, for this utility model, the turbine made of aluminum alloy is milled using a five-axis machine tool, and the material can be high-strength aluminum alloys such as 2618 (2618A) or 2A70; the machining of the rotor shaft 2 and the machining of the shaft end locking nut 3 can both be carried out using traditional machining methods, and the material can be alloy steel such as 40Cr or 42CrMo, which will not be elaborated here.

[0095] The fourth step is to assemble the turbine 1 made of the processed aluminum alloy material, the rotor shaft 2 and the shaft end locking nut 3 together to obtain the finished turbocharger turbine shaft. Then, the turbocharger turbine shaft is assembled into a turbocharger and the turbocharger is used as a low temperature test machine for the turbocharger. That is, the fourth step is to complete the assembly of the turbine shaft and the turbocharger assembly of the turbine shaft.

[0096] It should be noted that, for this utility model, a turbine shaft with an aluminum alloy turbine is used to replace the traditional turbine shaft installation position in the original turbocharger, thus completing the assembly of the low-temperature performance turbocharger testing machine.

[0097] The fifth step is to use a turbocharger cryogenic test bench to perform performance tests on the turbocharger turbine shaft in the turbocharger cryogenic test machine and obtain performance data of the turbocharger turbine shaft.

[0098] It should be noted that a turbocharger cryogenic test bench was used, and existing mature and conventional testing methods were employed to test the turbocharger turbine shaft in the turbocharger cryogenic test machine. Since this test machine is equipped with a turbine shaft with an aluminum alloy turbine, laboratory data on turbine performance were ultimately obtained.

[0099] It should be noted that, in this invention, the turbine performance test refers to a turbine flow characteristic test. This test measures the physical properties of the gas before and after passing through the turbine blade passage (including: gas temperature at the inlet, gas pressure at the inlet, gas temperature at the outlet, gas pressure at the outlet, and mass flow rate of the gas passing through the passage). Using thermodynamic formulas, parameters reflecting turbine performance, such as the expansion ratio, similar flow rate, and efficiency, are calculated. These parameters can be used to evaluate the performance of different turbines and serve as a basis for turbine blade design optimization.

[0100] In this invention, the low-temperature performance test differs from the traditional high-temperature performance test (600-650℃). The test temperature is selected as (50-200℃). Under this temperature condition, the aluminum alloy turbine can work normally, and the turbine flow characteristic test can be completed to obtain turbine performance data.

[0101] In practice, turbine performance testing is conducted on a well-established and technically mature dedicated turbocharger performance test bench. This bench precisely controls the turbine intake temperature, using hot air to drive the turbine. Sensors are installed at the turbine inlet and outlet to measure parameters such as temperature, pressure, and flow rate. The turbine intake temperature meets the requirements for low-temperature testing. Low-temperature intake conditions can be achieved using electrically heated air devices or natural gas combustion heating for temperature control, ensuring stable low-temperature intake conditions for turbine performance testing.

[0102] In practice, turbine performance tests are conducted under preset speed conditions, with 5-6 constant speed lines selected from low to high test speeds. Measurement points at different speeds are selected between the compressor's maximum flow point (close to the blockage flow) and minimum flow point (close to the surge flow). 6-7 points are evenly selected for each speed line according to the flow rate, and parameters such as temperature, pressure, and mass flow rate at the turbine inlet and outlet are measured. Finally, turbine performance parameters such as expansion ratio, similar flow rate, and efficiency are calculated.

[0103] In specific implementation of this invention, by analyzing and comparing the low-temperature performance data of different turbine blades, the performance advantages and disadvantages of different turbines can be easily confirmed, which can serve as an important basis for turbine blade design.

[0104] Compared with existing technologies, the turbocharger turbine shaft and testing method provided by this invention can achieve low-cost acquisition of turbine blade performance data, and has the following beneficial effects:

[0105] 1. The turbine shaft of this utility model can use the same turbine blade design data as the turbine shaft manufactured by traditional casting turbine to process aluminum alloy impellers. The test performance of aluminum alloy blades can replace the test performance of casting turbines.

[0106] 2. The turbine shaft of this utility model can replace the original turbine shaft for turbocharger assembly without any changes, and can be replaced in situ.

[0107] 3. The turbine shaft of this utility model uses an aluminum alloy turbine for low-temperature performance testing. Since aluminum alloy has a low operating temperature, the turbine performance test temperature needs to be below 250℃. Usually, the turbine test temperature is selected between 50-200℃. According to the principle of thermodynamic fluid similarity, the turbine blade performance is the same when tested at high temperature and low temperature. Therefore, the aluminum alloy turbine shaft used in this utility model for low-temperature testing can replace the traditional cast turbine shaft used for high-temperature testing.

[0108] 4. The turbine shaft of this utility model uses an aluminum alloy turbine and a shaft end nut connection method to combine the turbine shaft, which reduces the time-consuming and costly manufacturing links such as the manufacturing of the turbine mold, the precision casting process of the turbine, and the welding process of the turbine shaft. The production cost is low and the manufacturing cycle is significantly shortened. This can well meet the need to save the actual performance verification time of the turbine blade, accelerate the turbine blade performance development process, and reduce the turbine production and manufacturing cost. Compared with the traditional turbine verification cycle, the turbine development efficiency of this utility model is increased by 80% and the verification cost is reduced by 90%. The turbine blades verified by the aluminum alloy turbine shaft can be used for the production of turbine shafts for the final high-temperature alloy cast turbine.

[0109] 5. The turbine shaft of this utility model is mainly used in the turbine blade performance data acquisition and turbine blade performance verification stage. Due to the temperature limitation of aluminum alloy turbines, the turbine shaft of the traditional cast turbine cannot be used in the final turbocharger. The turbine of this utility model can be used for low temperature performance testing, which accelerates the turbocharger performance design progress and is a means to improve the turbocharger turbine performance design cycle.

[0110] 6. As an extension of this utility model, the aluminum alloy turbine can be machined using titanium-aluminum alloy. The use of titanium-aluminum alloy to machine the turbine further expands the application value of the turbine shaft structure of this utility model. Because titanium-aluminum alloy has a high operating temperature, it can meet the requirements of use under high temperature conditions and can replace the integral turbine shaft. It has the technical advantages of light weight and low moment of inertia. Therefore, in certain product application scenarios, titanium-aluminum alloy turbine shafts have further application value, and these applications also reflect the extended value of this utility model.

[0111] In summary, compared with the prior art, this utility model provides a turbocharger turbine shaft with a scientific design, which is conducive to quickly and reliably obtaining turbine blade performance data, thereby rapidly verifying whether the turbine blade performance data meets the pre-required design indicators, significantly saving time and costs, improving the efficiency of turbine design and development, and has significant practical significance.

[0112] Furthermore, this invention provides a low-cost and rapid technical solution for obtaining turbine blade performance test results. It allows the use of a low-cost aluminum alloy turbine instead of a traditional cast turbine to manufacture the turbine shaft, thereby enabling rapid acquisition of turbine blade performance through testing.

[0113] Therefore, the present invention provides a turbocharger turbine shaft with an aluminum alloy turbine, which can replace the traditionally designed turbine shaft for low-temperature turbine performance testing. It has low production cost, short production cycle, and can significantly improve the development progress of turbine blade performance, resulting in huge economic benefits.

[0114] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A turbocharger turbine shaft, characterized in that, It is used in turbine performance testing and includes a turbine (1), a rotor shaft (2) and a shaft end locking nut (3); The rotor shaft (2) is detachably and fixedly connected to the rotor shaft (2) by a shaft end locking nut (3); Among them, the turbine (1) includes a turbine hub (11); The turbine hub (11) has a longitudinally distributed central through hole (12) at its center; Multiple turbine blades (13) are distributed around the front surface of the turbine hub (11); Multiple turbine blades (13) are evenly distributed around the vertical central axis (14) of the turbine hub (11) in the circumferential direction. Among them, the rotor shaft (2) is a stepped shaft structure; The front and middle sections of the rotor shaft (2) have a rotor shaft body (20); The front end of the rotor shaft body (20) has an external thread section (21) and a mounting shaft section (23); The mounting shaft section (23) is located behind the external thread section (21); The mounting shaft section (23) is longitudinally inserted through the center through hole (12) of the turbine (1); The external thread section (21) is used to lock the turbine (1) together with the shaft end lock nut (3); The rotor shaft body (20) has a positioning step (22) in the middle; The positioning step (22) is used to position and support the turbine (1); Multiple turbine blades (13) are identical in shape and size; For the turbine (1), each turbine blade (13) has a blade inlet edge (131) on the side away from the turbine hub (11); The rear end of the blade intake edge (131) is fixedly connected to the front surface of the turbine hub (11); Each turbine blade (13) has a blade outlet edge (132) on one side near the front end face of the turbine hub (11); The inner end of the blade outlet edge (132) is fixedly connected to the front surface of the turbine hub (11).

2. The turbocharger turbine shaft as described in claim 1, characterized in that, The blade inlet edge (131) serves as the turbine inlet leading edge, and its shape and structure are parallel to the vertical central axis (14) of the turbine hub (11).

3. The turbocharger turbine shaft as described in claim 1 or 2, characterized in that, The blade inlet edge (131) serves as the turbine inlet leading edge, and its shape and structure are inclined structures that are not parallel to the vertical central axis (14) of the turbine hub (11). The angle between the blade inlet edge (131) and the vertical central axis (14) of the turbine hub (11) is 0 to 40 degrees.

4. The turbocharger turbine shaft as described in claim 1, characterized in that, The front end face of the hub (11) is a hub planar structure (15); The hub planar structure (15) is used to contact the end face planar structure (31) behind the shaft end locking nut (3) and the two are connected by a fixed torque.

5. The turbocharger turbine shaft as described in claim 1, characterized in that, For the rotor shaft (2), the external thread section (21) is used to lock the turbine (1) together with the shaft end locking nut (3). The specific structural design is as follows: The external thread of the external thread section (21) is fixedly connected to the internal thread structure (32) of the shaft end locking nut (3).

6. The turbocharger turbine shaft as described in claim 1, characterized in that, The diameter of the positioning step (22) is larger than the diameter of the central through hole (12) of the turbine (1); The front surface of the positioning step (22) is a plane; The mounting shaft section (23) is fitted with the center through hole (12) of the turbine (1) for installation; The mounting shaft section (23) and the center through hole (12) of the turbine (1) are transition fit.

7. The turbocharger turbine shaft as described in any one of claims 1 to 6, characterized in that, The shaft end locking nut (3) includes a rear end face planar structure (31) and an internal thread structure (32) located at the center. The internal thread structure (32) is an internal thread hole that passes vertically through the shaft end lock nut (3).

8. The turbocharger turbine shaft as described in any one of claims 1 to 7, characterized in that, The turbine (1) is made of aluminum alloy and is machined by five-axis milling. The rotor shaft (2) is made of alloy steel; The material of the shaft end locking nut (3) is alloy steel; The turbocharger turbine shaft is used in low-temperature performance testing, which requires a test temperature range of 50–200°C.

9. The turbocharger turbine shaft as described in claim 4, characterized in that, The turbine (1) is made of 2618 or 2A70 aluminum alloy; The rotor shaft (2) is made of 40Cr or 42CrMo alloy steel; The material of the shaft end locking nut (3) is 40Cr or 42CrMo alloy steel.

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